Assembly comprising a gas turbine combustion chamber integrated with a high pressure turbine nozzle
View Patent ↗The high pressure turbine nozzle is mechanically connected to a downstream end portion of the combustion chamber and inner and outer connection ferrules connect the combustion chamber and turbine nozzle assembly to inner and outer metal shrouds in order to hold said assembly between the shrouds. Locking members are provided to prevent the turbine nozzle from turning about its axis relative to at least one of the metal shrouds so as to prevent the forces that are exerted on the turbine nozzle vanes by the flow of gas coming from the chamber being taken up by the portions of the connection ferrules that extend between the combustion chamber and turbine nozzle assembly and the metal shrouds.
1. A gas turbine comprising:
an annular combustion chamber having a wall made of ceramic matrix composite material;
a high pressure turbine nozzle having a plurality of stationary vanes distributed around an axis coinciding with the axis of the combustion chamber, the turbine nozzle being mechanically connected to a downstream end portion of the combustion chamber so as to from an assembly together therewith;
inner and outer metal shrouds between which the assembly constituted by the combustion chamber and the turbine nozzle is housed;
flexible inner and outer connection ferrules connecting the combustion chamber and turbine nozzle assembly respectively to the inner and outer metal shrouds so as to support said assembly between the shrouds; and
locking members preventing the turbine nozzle from turning about its own axis relative to at least one of the metal shrouds so as to avoid the forces that are exerted on the turbine nozzle vanes by the flow of gas from the chamber being taken up by the portions of the connection ferrules that extend between the combustion chamber and turbine nozzle assembly and the metal shrouds.
2. A gas turbine according to claim 1 , wherein the locking members co-operate with a wall portion secured to a metal shroud, and a flange secured to the turbine nozzle.
3. A gas turbine according to claim 2 , wherein the wall portion secured to the metal shroud is in the form of a radial flange.
4. A gas turbine according to claim 2 , wherein the locking members act on a radial flange secured to a metal shroud and a radial flange secured to the turbine nozzle between which there is housed an annular sealing gasket.
5. A gas turbine according to claim 4 , wherein the locking members comprise axial rods for retaining the sealing gasket.
6. A gas turbine according to claim 2 , wherein the flange secured to the turbine nozzle is carried by a connection ferrule at an end thereof that is fastened to the turbine nozzle.
7. A gas turbine according to claim 2 , wherein first locking members are provided acting between a radial flange secured to the inner metal shroud and an inner radial flange secured to the turbine nozzle, and second locking members are provided acting between a radial flange secured to the outer metal shroud and an outer radial flange secured to the turbine nozzle.
8. A gas turbine according to claim 1 , wherein downstream end portions of the combustion chamber are clamped between platforms of the turbine nozzle vanes and end portions of the connection ferrules by fastener members connecting together the connection ferrules, the combustion chamber, and the turbine nozzle.
9. A gas turbine according to claim 1 , wherein the connection ferrules are made at least in part out of a ceramic matrix composite material.